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41. 发明授权

US07419353B2 Blade of a turbomachine with block-wise defined profile skeleton line 有权
标题翻译：具有块状定义轮廓骨架线的涡轮机叶片
公开(公告)号：US07419353B2
公开(公告)日：2008-09-02
申请号：US11510826
申请日：2006-08-28
申请人： Volker Guemmer
发明人： Volker Guemmer
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , F01D5/145 , F04D29/544 , F05D2240/301 , F05D2250/71 , Y10S416/02
摘要： A turbomachine blade with a profile skeleton line extending along a meridional flow line, the blade being radially divided into at least three zones (Z0, Z1, Z2) with profile skeleton lines of each zone (Z0, Z1, Z2) provided in each zone from the respective radially inner to the radially outer boundary to satisfy the equations: α * = α 1 - α P α 1 - α 2 S * = s P S where P is any point of the profile skeleton line, α1 is angle of inclination at blade leading edge, α2 is angle of inclination at blade trailing edge, α* is dimensionless, specific angle of total curvature, S* is dimensionless; specific extension, αP is angle of tangent at any point P of profile skeleton line to central meridional flow line, sP is extension of profile skeleton line at any point P, and S is total extension of profile skeleton line.
摘要翻译：一种涡轮机叶片，具有沿着子午线流线延伸的轮廓骨架线，叶片径向分成至少三个区域（Z 0，Z 1，Z 2），每个区域的轮廓骨架线（Z 0，Z 1，Z 2）设置在每个区域中从各自的径向内部到径向外边界以满足以下等式： $MSUP> alpha*=1_{-alphaP>_{< > S*=S其中P是轮廓骨架线的任何点， / SUB>是叶片前缘处的倾斜角，α2是刀片后缘处的倾斜角，α*是无量纲的，总曲率的特定角度，S *是无量纲的; 特定的延伸部分是轮廓骨架线到中心子午线的任何点P处的切线角，是在任何点P处轮廓骨架线的延伸， S是轮廓骨架线的总延伸。}}$

42. 发明授权

US07351039B2 Compressor rotor blade 有权
标题翻译：压缩机转子叶片
公开(公告)号：US07351039B2
公开(公告)日：2008-04-01
申请号：US10983225
申请日：2004-11-08
申请人： René Bachofner , Wolfgang Kappis
发明人： René Bachofner , Wolfgang Kappis
IPC分类号： F04D29/38
CPC分类号： F04D29/668 , F01D5/141 , F01D5/16 , F01D5/20 , F04D29/324 , F05D2240/301
摘要： A compressor rotor blade (1) includes a rotor blade (2), a platform (3) that adjoins the rotor blade (2) and blade footing (4) that adjoins the platform (3). The rotor blade (4) is embodied so as to be massive, without an internal cooling system, and exhibits a leading and a trailing edge (5, 6), a suction and a compression side, as well as a blade tip (7). The compressor rotor blade (1) is distinguished by virtue of the fact that the rotor blade (2) of the compressor rotor blade (1) exhibits a recess (8) on the trailing edge (6) of the blade tip (7).
摘要翻译：压缩机转子叶片（1）包括转子叶片（2），与转子叶片（2）相邻的平台（3）和邻接平台（3）的叶片基部（4）。转子叶片（4）被实施为具有巨大的，没有内部冷却系统，并且具有前缘和后缘（5,6），吸力和压缩侧以及叶片尖端（7）。压缩机转子叶片（1）的特征在于压缩机转子叶片（1）的转子叶片（2）在叶片尖端（7）的后缘（6）上具有凹部（8）。

43. 发明授权

US07316539B2 Vane assembly with metal trailing edge segment 有权
标题翻译：具有金属后缘段的叶片组件
公开(公告)号：US07316539B2
公开(公告)日：2008-01-08
申请号：US11101255
申请日：2005-04-07
申请人： Christian X. Campbell
发明人： Christian X. Campbell
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/146 , F05D2240/301 , F05D2240/57 , F05D2260/20 , F05D2260/221 , F05D2300/21 , F05D2300/603
摘要： Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. The forward and aft segments cannot be directly joined to each other because of differences in their rates of thermal expansion and contraction. The forward and aft segments can be positioned substantially proximate to each other so as to form a gap therebetween. In one embodiment, the gap can be substantially sealed by providing a coupling insert or leaf springs in the gap. A separate metal aft segment can take advantage of the beneficial thermal properties of the metal to improve cooling efficiency at the trailing edge without limiting the rest of the vane to being made out of metal.
摘要翻译：本发明的实施例涉及由前部翼型段和后部翼型段形成的叶片组件。后段由金属制成并且可以限定叶片组件的后缘。前段可由陶瓷，CMC或金属制成。由于其热膨胀和收缩率的差异，前部和后部部分不能彼此直接连接。前段和后段可以基本上彼此靠近地定位，以便在它们之间形成间隙。在一个实施例中，通过在间隙中设置联接插件或板簧可以实现密封。单独的金属后部段可以利用金属的有益的热性质来提高后缘处的冷却效率，而不会限制叶片的其余部分被制成金属。

44. 发明申请

US20070140837A1 Turbomachine with variable stator 有权
公开(公告)号：US20070140837A1
公开(公告)日：2007-06-21
申请号：US11640404
申请日：2006-12-18
申请人： Volker Guemmer
发明人： Volker Guemmer
IPC分类号： F04D29/56
CPC分类号： F04D29/563 , F01D5/141 , F01D17/165 , F04D29/544 , F05D2240/301 , F05D2250/00 , F05D2250/14 , F05D2250/74 , Y10S416/02
摘要： A variable stator of a turbomachine with a profile skeleton line extending along a meridional flow line, with the stator being radially divided into at least three zones (Z0, Z1, Z2) and with the respective radial inner and the radial outer profile skeleton line of each zone (Z0, Z1, Z2) being designed such that it satisfies the following equations: α * = α 1 - α P α 1 - α 2 S * = S P S where: P is any point of the profile skeleton line, α1 is the angle of inclination at the stator leading edge, α2 is the angle of inclination at the stator trailing edge, α* is the dimensionless, specific angle of the total curvature, S* is the dimensionless, specific extension, αp is the angle of the tangent at any point P of the profile skeleton line to the central meridional flow line, sp is the extension of the profile skeleton line at any point P, and S is the total extension of the profile skeleton line.

45. 发明授权

US07186090B2 Air foil shape for a compressor blade 失效
标题翻译：用于压缩机叶片的气翼形状
公开(公告)号：US07186090B2
公开(公告)日：2007-03-06
申请号：US10986162
申请日：2004-11-12
申请人： Steven Eric Tomberg , Roger Beharrysingh , Timothy E. DeJoris , William J. Miller , Paul Deivernois , Venkata Siva P. Chaluvadi , Adrian Mircea Mistreanu , Michael James Dutka , Nathan S. Race , Jeffrey Boyd , Christopher David McGowan , Peter Gaines Cleveland , Jason Thomas Harrell , Carl G. Schott , John David Stampfli , Ronald Stuart Denmark , Steven Mark Schirle , Jennifer B. Michenfelder , John F. Ryman
发明人： Steven Eric Tomberg , Roger Beharrysingh , Timothy E. DeJoris , William J. Miller , Paul Deivernois , Venkata Siva P. Chaluvadi , Adrian Mircea Mistreanu , Michael James Dutka , Nathan S. Race , Jeffrey Boyd , Christopher David McGowan , Peter Gaines Cleveland , Jason Thomas Harrell , Carl G. Schott , John David Stampfli , Ronald Stuart Denmark , Steven Mark Schirle , Jennifer B. Michenfelder , John F. Ryman
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/301 , Y10S416/02 , Y10S416/05
摘要： An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S–16S, 1R–17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译：一种具有基本上符合表中列出的X，Y和Z的笛卡尔坐标值的公称轮廓的制品。该表从由表1S-16S，1R-17R和IGV组成的表格中选择。其中X和Y是以英寸为单位的距离，当通过平滑连续的弧连接时，以每英寸的距离Z限定翼型轮廓部分。 Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型形状。

46. 发明授权

US07094034B2 Airfoil profile with optimized aerodynamic shape 有权
公开(公告)号：US07094034B2
公开(公告)日：2006-08-22
申请号：US10903803
申请日：2004-07-30
申请人： Takao Fukuda , Francis R. Price , Shankar S. Magge
发明人： Takao Fukuda , Francis R. Price , Shankar S. Magge
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/3212 , F05D2240/301 , F05D2250/74 , Y10S416/02 , Y10S416/05
摘要： Provided is an aerodynamic profile for use in gas turbine airfoil and a turbine blade comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches. The R values are measured perpendicular to a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.

47. 发明申请

US20050207893A1 Aerodynamically wide range applicable cylindrical blade profiles 失效
标题翻译：空气动力范围广泛的圆柱形刀片型材
公开(公告)号：US20050207893A1
公开(公告)日：2005-09-22
申请号：US10861602
申请日：2004-06-04
申请人： A. L. Chandraker
发明人： A. L. Chandraker
IPC分类号： B63H1/26
CPC分类号： F01D5/141 , F05D2220/31 , F05D2240/301 , F05D2250/231 , F05D2250/70 , Y10S416/02 , Y10S416/05
摘要： The present invention relates to the improved aerodynamic design of a pair of blade profiles valid over a wide range of flow regime. The so formed blades, pertain to high pressure, intermediate pressure and first few stages of low pressure cylinders of axial steam turbines. The invented blades cover a wide range of stagger angles; pitch/chord ratios; inlet flow angles and outlet Mach numbers.
摘要翻译：本发明涉及在宽范围的流动状态下有效的一对叶片轮廓的改进的空气动力学设计。这样形成的叶片涉及高压，中压和轴流蒸汽轮机的低压缸的前几个阶段。本发明的刀片覆盖了广泛的交错角度; 音高/弦比; 入口流量角和出口马赫数。

48. 发明申请

US20050106030A1 Compressor rotor blade 有权
标题翻译：压缩机转子叶片
公开(公告)号：US20050106030A1
公开(公告)日：2005-05-19
申请号：US10983225
申请日：2004-11-08
申请人： Rene Bachofner , Wolfgang Kappis
发明人： Rene Bachofner , Wolfgang Kappis
IPC分类号： F01D5/14 , F01D5/16 , F01D5/20 , F04D29/32 , F04D29/66 , B63H7/02
CPC分类号： F04D29/668 , F01D5/141 , F01D5/16 , F01D5/20 , F04D29/324 , F05D2240/301
摘要： A compressor rotor blade (1) includes a rotor blade (2), a platform (3) that adjoins the rotor blade (2) and blade footing (4) that adjoins the platform (3). The rotor blade (4) is embodied so as to be massive, without an internal cooling system, and exhibits a leading and a trailing edge (5, 6), a suction and a compression side, as well as a blade tip (7). The compressor rotor blade (1) is distinguished by virtue of the fact that the rotor blade (2) of the compressor rotor blade (1) exhibits a recess (8) on the trailing edge (6) of the blade tip (7).
摘要翻译：压缩机转子叶片（1）包括转子叶片（2），与转子叶片（2）相邻的平台（3）和邻接平台（3）的叶片基部（4）。转子叶片（4）被实施为具有巨大的，没有内部冷却系统，并且具有前缘和后缘（5,6），吸力和压缩侧以及叶片尖端（7）。压缩机转子叶片（1）的特征在于压缩机转子叶片（1）的转子叶片（2）在叶片尖端（7）的后缘（6）上具有凹部（8）。

49. 发明申请

US20050079061A1 AIRFOIL SHAPE FOR A TURBINE BUCKET 有权
标题翻译：用于涡轮马桶的气翼形状
公开(公告)号：US20050079061A1
公开(公告)日：2005-04-14
申请号：US10681144
申请日：2003-10-09
申请人： Thomas Beddard , David Pesetsky
发明人： Thomas Beddard , David Pesetsky
IPC分类号： F01D5/06 , F01D5/14 , B63H1/26
CPC分类号： F01D5/141 , F05D2240/301 , F05D2250/50 , Y10S416/02 , Y10S416/05
摘要： Second stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0.05 to 0.95 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.160 inches in directions normal to the surface of the airfoil.
摘要翻译：第二级涡轮机叶片具有基本上符合X，Y和Z的笛卡尔坐标值的翼型轮廓，其中X和Y值为英寸，Z值为0.05至0.95，可转换为Z距离的无量纲值将Z值乘以翼型件的高度（英寸）。 X和Y值是通过平滑连续弧连接时定义每个距离Z处的翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的翼型形状。作为相同常数或数字的函数，X和Y距离可以是可缩放的，以提供用于铲斗的放大或缩小的翼型部分。由X，Y和Z距离给出的额定翼型在垂直于翼面表面的方向上在±0.160英寸的范围内。

50. 发明授权

US06779980B1 Airfoil shape for a turbine bucket 有权
标题翻译：涡轮叶片的翼型
公开(公告)号：US06779980B1
公开(公告)日：2004-08-24
申请号：US10386676
申请日：2003-03-13
申请人： Robert Alan Brittingham , Edward Durell Benjamin , Jacob Charles Perry, II , Craig Allen Bielek
发明人： Robert Alan Brittingham , Edward Durell Benjamin , Jacob Charles Perry, II , Craig Allen Bielek
IPC分类号： F01D514
CPC分类号： F01D5/14 , F01D5/187 , F05D2240/301 , Y10S416/02 , Y10S416/05
摘要： First stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.040 inches in directions normal to the surface of the airfoil.
摘要翻译：第一级涡轮机叶片具有基本上符合X，Y和Z的笛卡尔坐标值的翼型轮廓，其中X和Y值以英寸计，Z值是从0到1可转换成Z距离的无量纲值将Z值乘以翼型件的高度（英寸）。 X和Y值是通过平滑连续弧连接时定义每个距离Z处的翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的翼型形状。 X，Y和Z距离可以作为相同常数或数字的函数来缩放，以提供用于铲斗的放大或缩小的翼型部分。由X，Y和Z距离给出的额定翼型在垂直于翼面表面的方向上处于±0.040英寸的包络内。

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